Готові списки джерел за темами / Interlaminar transverse shear

Добірка наукової літератури з теми "Interlaminar transverse shear"

Автор: Grafiati

Опубліковано: 14 березня 2023

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Статті в журналах з теми "Interlaminar transverse shear"

Lu, Xianqiang, and Dahsin Liu. "An Interlaminar Shear Stress Continuity Theory for Both Thin and Thick Composite Laminates." Journal of Applied Mechanics 59, no. 3 (September 1, 1992): 502–9. http://dx.doi.org/10.1115/1.2893752.

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Анотація:

The interlaminar shear stress plays a very important role in the damage of composite laminates. With higher interlaminar shear stress, delamination can easily occur on the composite interface. In order to calculate the interlaminar shear stress, a laminate theory, which accounts for both the interlaminar shear stress continuity and the transverse shear deformation, was presented in this study. Verification of the theory was performed by comparing the present theory with Pagano’s elasticity analysis. It was found that the present theory was able to give excellent results for both stresses and displacements. More importantly, the interlaminar shear stress can be presented directly from the constitutive equations instead of being recovered from the equilibrium equations.

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Wang, Xiao Dan, and Guang Yu Shi. "Evaluation of Various Laminated Plate Theories Accounting for Interlaminar Transverse Shear Stress Continuity." Advanced Materials Research 716 (July 2013): 119–26. http://dx.doi.org/10.4028/www.scientific.net/amr.716.119.

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Based on a unified form of the plate kinematics in terms of the transverse shear functions and the Heaviside step function, the analytical solutions of laminated plates corresponding to a number of higher-order shear deformation plate theories are solved in this paper. The accuracy assessment of these higher-order laminated plate theories is conducted by comparing the resulting analytical solutions with the elasticity solutions and finite element results. The accuracy study shows that the interlaminar shear stress continuity condition is very important for the accurate prediction of the transverse shear stresses across the laminated plate thickness. The comparison study also indicates that the new laminated plate theory accounting for the interlaminar transverse shear stress continuity proposed by the authors yields both very accurate displacements and accurate stresses. This new higher-order laminated plate theory can be efficiently used in the finite element analysis of laminated composite plates since it uses the same five field variables as those used in the first-order shear deformation plate theory.

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Popper, P., C. Miller, D. L. Filkin, and W. J. Schaffers. "A Simple Model for Cornering and Belt-edge Separation in Radial Tires." Tire Science and Technology 14, no. 1 (January 1, 1986): 3–32. http://dx.doi.org/10.2346/1.2148765.

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Abstract A mathematical analysis of radial tire cornering was performed to predict tire deflections and belt-edge separation strains. The model includes the effects of pure bending, transverse shear bending, lateral restraint of the carcass on the belt, and shear displacements between belt and carcass. It also provides a description of the key mechanisms that act during cornering. The inputs include belt and carcass cord properties, cord angle, pressure, rubber properties, and cornering force. Outputs include cornering deflections and interlaminar shear strains. Key relations found between tire parameters and responses were the optimum angle for minimum cornering deflections and its dependence on cord modulus, and the effect of cord angle and modulus on interlaminar shear strains.

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Whitney, James M., and Anis Gawandi. "Effective interlaminar shear moduli in composites containing transverse ply cracks." Composites Science and Technology 66, no. 14 (November 2006): 2591–98. http://dx.doi.org/10.1016/j.compscitech.2006.01.005.

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Zhen, Wu, and Chen Wanji. "Interlaminar stress analysis of multilayered composites based on the Hu-Washizu variational theorem." Journal of Composite Materials 52, no. 13 (September 27, 2017): 1765–79. http://dx.doi.org/10.1177/0021998317733532.

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Up to date, accurate prediction of interlaminar stresses is still a challenging issue for two-node beam elements. The postprocessing approaches by integrating the three-dimensional equilibrium equation have to be used to obtain improved transverse shear stresses, whereas the equilibrium approach requires the first-order derivatives of in-plane stresses. In-plane stresses within two-node beam element are constant, so the first-derivatives of in-plane stresses are close to zero. Thus, two-node beam elements encounter difficulties for accurate prediction of transverse shear stresses by the constitutive equation or the equilibrium equation, so a robust two-node beam element is expected. A two-node beam element in terms of the global higher-order zig-zag model is firstly developed by employing the three-field Hu-Washizu mixed variational principle. By studying the effects of different boundary conditions, stacking sequence and loading on interlaminar stresses of multilayered composite beams, it is shown that the proposed two-node beam element yields more accurate results with lesser computational cost compared to various higher-order models. It is more important that accurate transverse shear stress has active impact on displacements and in-plane stresses of multilayered composite beams.

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Carrera, E. "A Reissner’s Mixed Variational Theorem Applied to Vibration Analysis of Multilayered Shell." Journal of Applied Mechanics 66, no. 1 (March 1, 1999): 69–78. http://dx.doi.org/10.1115/1.2789171.

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A comprehensive model of anisotropic multilayered double curved shells fulfilling a priori the interlaminar continuity requirements for the transverse shear and transverse normal stress as well as the static conditions on the bounding surfaces of the shell is developed in this paper. To this end, Reissner’s mixed variational theorem is employed to derive the equations governing the dynamic equilibrium and compatibility of each layer, while the interlaminar continuity conditions are used to drive the equations at the multilayered level. No assumptions have been made concerning the terms of type thickness to radii shell ratio h/R. Classical displacement formulations and related equivalent single layer equations have been derived for comparison purposes. Comparison of frequency predictions based upon the presented structural model with a number of results spread throughout the specialized literature and obtained via other models reveals that this advanced model provides results in excellent agreement with the ones based on three-dimensional elasticity theory, and better as compared to the ones violating the interlaminar stress continuity requirements and/or transverse normal stress and related effects.

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Koziol, Mateusz. "Experimental study on the effect of stitch arrangement on mechanical performance of GFRP laminates manufactured on a basis of stitched preforms." Journal of Composite Materials 46, no. 9 (October 4, 2011): 1067–78. http://dx.doi.org/10.1177/0021998311414947.

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This article presents the results of interlaminar shear and flexural tests of stitched polyester glass fiber laminates in dependence on stitch density and main geometric stitching parameters: stitch length and stitch spacing. Purpose of the study is to work out guidelines and indications for manufacturers of composite laminates who use or who plan to use stitching technique. It was found that stitching significantly improves interlaminar shear strength which increases with stitch density. However, stitching causes deterioration of in-plane flexural properties – the deterioration progresses when stitch density increases. Obtained results indicate that it is better to achieve increase in stitch density (resulting in improvement of interlaminar shear strength) by reduction of stitch length than by reduction of stitch spacing. Stitched laminate shows higher flexural strength and flexural modulus when bent into direction parallel to the stitch lines than when bent into the transverse direction. The results obtained within the study and their approximation constants may be a base for a new theoretical model simulating behavior of stitched laminate during static bending and enabling prediction of its mechanical performance.

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Woelke, Pawel, Ka-Kin Chan, Raymond Daddazio, Najib Abboud, and George Z. Voyiadjis. "Analysis of Shear Flexible Layered Isotropic and Composite Shells by ‘EPSA’." Shock and Vibration 19, no. 3 (2012): 459–75. http://dx.doi.org/10.1155/2012/179879.

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We present a simple and efficient method for the analysis of shear flexible isotropic and orthotropic composite shells. Classical thin shell constitutive equations used in the explicit finite element code EPSA to model homogenous isotropic shells using "through-the-thickness-integration" and layered orthotropic composite shells [1–3,5] are modified to account for transverse shear deformation. This effect is important in the analysis of thick plates and shells as well as composite laminates, where interlaminar effects matter. Transverse shear stresses are calculated using a linear normal strain distribution, where first the shear forces are calculated and then the stresses are calculated by means of the generalized section properties, i.e., first and second moments of area. The formulation is a generalization of the analytical method of analyzing composite beams. It is simple and computationally inexpensive, and it yields accurate results without employing higher order displacement interpolations. In the case of isotropic shells, the transverse shear stresses are distributed parabolically, based on the assumption of linear normal strain distribution through the thickness and on application of the quadratic shape function to transverse shear strains. The transverse shear stresses are included in the elastic-perfectly plastic yield function of the Huber-Mises-Hencky type.

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Luo, Quantian, and Liyong Tong. "Energy release rates for interlaminar delamination in laminates considering transverse shear effects." Composite Structures 89, no. 2 (June 2009): 235–44. http://dx.doi.org/10.1016/j.compstruct.2008.07.015.

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Ziao, J., and J. Tao. "Investigation of Interlaminar Defects and their Influence on Interlaminar Strength." Advanced Composites Letters 5, no. 4 (July 1996): 096369359600500. http://dx.doi.org/10.1177/096369359600500404.

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In this paper, we directed our attention to the interlaminar defects and their influence on the interlaminar strengths. With the aid of a S-570 scanning electron microscope, the morphology and distribution of interlaminar defects were inspected and documented. According to their shape, size and cause of formation, the defects were classified into five types: flakiness void, irregular shaped debond, local imperfectly cured resin, debond in two multi-directional plies, and inhomogeneous fibers and the large scale debond by these fibers. The cause of defects formation was discussed by analyzing the manufacturing process of composites. The influence of defects on the interlaminar strength and its mechanism was analyzed experimentally and theoretically. The results indicate that these defects, with different effects, decrease the interlaminar strength because they form interlaminar cracks, and the interlaminar shear strength is less affected than interlaminar tensile strength, which is measured according to GB4944 test method. To comprehend defects distribution effect, a four-point-bending test method was introduced to measure the interlaminar peel strength, and a discussion was made on the correlation between the interlaminar tensile strength, interlaminar peel strength and in-plane transverse tensile strength. Finally the concept of interlaminar defect coefficient, which can be used to characterize the defects, was set up and the formula to calculate it was proposed.

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Дисертації з теми "Interlaminar transverse shear"

URRACI, ANDREA. "Development of accurate and efficient structural models for analysis of multilayered and sandwich structures of industrial interest." Doctoral thesis, Politecnico di Torino, 2020. http://hdl.handle.net/11583/2829677.

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Книги з теми "Interlaminar transverse shear"

Li, Jian. Simplified data reduction methods for the ECT test for mode III interlaminar fracture toughness. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

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Тези доповідей конференцій з теми "Interlaminar transverse shear"

Steinbrink, Scott E. "On a Proposed New Kinematic Assumption for Analysis of Laminated, Fiber-Reinforced Composite Shells: Part 1." In ASME 2003 Pressure Vessels and Piping Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/pvp2003-1914.

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A proposal is made for a new form of kinematic assumption for inclusion into a theory of laminated shells. The proposed form is a variant of the first-order transverse shear deformation theory, incorporating a stiffness-based discontinuity term at lamina interfaces, in order to provide complete, a priori satisfaction of interlaminar continuity of transverse shear and transverse normal stresses, and correspondent intelaminar discontinuity of thickness-direction gradients of displacement. Continuity of displacement is maintained, as is the possibility of interlaminar discontinuity of in-plane stresses. It is hoped that this kinematic form will enhance the utility of shell theories for analysis of laminated structures. The paper deals only with the development of the kinematic assumption, and not its implementation into analysis code.

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Aly-Hassan, Mohamed S., Yuka Kobayashi, Asami Nakai, and Hiroyuki Hamada. "Tensile and Shear Properties of Biaxial Flat Braided Carbon/Epoxy Composites With Dispersed Carbon Nanofibers in the Matrix." In ASME 2008 2nd Multifunctional Nanocomposites and Nanomaterials International Conference. ASMEDC, 2008. http://dx.doi.org/10.1115/mn2008-47057.

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In laminated flat braided composites there are no fibers through the thickness direction except at the edges due to the fiber continuity of the braiding technique. A delamination along the interlaminar planes can be propagated because of the lack of fibers in the Z- or third-direction to the composite. The delamination initiates essentially as a result of arising the stresses concentrations around the transverse or matrix cracks that appear due to the mismatch of the thermal expansion coefficients of the fibers and matrix during the fabrication process. The delamination renders low interlaminar composite properties and represents a fundamental weakness of laminated flat braided composites especially with increasing the braiding angle, and thus minimizes the shear stress transfer. In this research, laminated flat braided carbon fabrics were performed via flattening tubular braided fabrics with braiding angle of ±45° by applying carefully compressive loads laterally on the tubular fabrics. Then, carbon fiber reinforced epoxy matrix composites were fabricated from the above-mentioned biaxial fabrics with and without uniformly dispersed carbon nanofibers throughout the epoxy matrix. Three loading percentages of carbon nanofibers (specifically, 0.5, 1, and 2 wt%) were dispersed in the matrix of the composites to enhance the matrix and interlaminar/inter-ply properties. The influence of matrix and interlaminar properties improvements on the in-plane tensile and shear response of the laminated flat braided composites was clarified via conducting of ±45° laminates tensile tests. The experimental results of tensile tests revealed that the tensile and in-plane shear properties as well as the fracture behavior of the composites are substantially influenced by the incorporation of the dispersed carbon nanofibers in the matrix of the composites. A pulsed thermography technique was used to inspect the occurrence of the delamination after the fracture under tensile loadings. The thermal wave image and logarithmic temperature-time curves of the pulsed thermography inspection illustrated that the composites with dispersed carbon nanofibers rendered higher interlaminar properties than that of composites without nanofibers. The main conclusion of this research can be summarized that dispersion of carbon nanofibers through the epoxy matrix of laminated flat braided composites is not only enhanced the matrix properties but also improved the interphase morphology between the composite plies that maximized the stress transfer of the composites. In other words, the fabricated braided composites with braiding angle of ±45° are predominantly by both of matrix and interlaminar properties.

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Carrera, Erasmo, Alberto García de Miguel, Alfonso Pagani, and Enrico Zappino. "Reissner’s Mixed Variational Theorem for Layer-Wise Refined Beam Models Based on the Unified Formulation." In ASME 2017 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/imece2017-71612.

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The present paper proposes the application of the Reissners Mixed Variational Theorem (RMVT) for the accurate stress analysis of general multi-layered beam problems. Laminated materials usually differ from homogeneous materials in that they exhibit much higher transverse shear and transverse normal deformabilities. These characteristics, and others such as the Transverse Anisotropy (TA) and the Interlaminar Continuity of transverse stresses (IC), make Classical Laminated Theories (CLT) inappropriate for the analysis of multi-layered structures. The Carrera Unified Formulation (CUF) sets a framework in which classical-to-refined beam models can be generated by expanding the unknown variables over the cross-sectional domain by means of arbitrary functions. A LW expansion is adopted for both displacements and transverse stresses over the cross-section section domain. In this manner, the ZZ condition is automatically satisfied through the use of independent kinematics for each layer in a LW sense, with no need of introducing ad-hoc ZZ functions.

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LIVINGSTON, ROBERT, and BEHRAD KOOHBOR. "IN SITU CHARACTERIZATION OF FIBER-MATRIX INTERFACE DEBONDING VIA FULL-FIELD MEASUREMENTS." In Thirty-sixth Technical Conference. Destech Publications, Inc., 2021. http://dx.doi.org/10.12783/asc36/35899.

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Macroscopic mechanical and failure properties of fiber-reinforced composites depend strongly on the properties of the fiber-matrix interface. For example, transverse cracking behavior and interlaminar shear strength of composites can be highly sensitive to the characteristics of the fiber-matrix interface. Despite its importance, experimental characterization of the mechanical behavior of the fibermatrix interface under normal loading conditions has been limited. This work reports on an experimental approach that uses in situ full-field digital image correlation (DIC) measurements to quantify the mechanical and failure behaviors at the fiber-matrix interface. Single fiber model composite samples are fabricated from a proprietary epoxy embedding a single glass rod. These samples are then tested under transverse tension. DIC is used to measure the deformation and strain fields in the glass rod, epoxy, and their interface vicinity. Initiation and propagation of the fiber-matrix debond are discussed. Full-field measurements are shown to facilitate the quantitative analysis of the traction-separation laws at the fiber-matrix interface subjected to transverse tension.

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Hosur, M. V., U. K. Vaidya, A. Abraham, and S. Jeelani. "Effect of 3D Reinforcement on the Low-Velocity Impact Response of S2-Glass/Vinyl Ester Composite Laminates." In ASME 1998 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/imece1998-0524.

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Abstract Due to their inherent weakness in thickness direction, laminated fiber reinforced composites are susceptible to undergo large delamination damage when subjected to transverse loading. Low-velocity impact loading is one such case. Low-velocity impact occurs due to tool-drops during manufacturing, maintenance, and service, runway debris during landing and takeoff and hailstorm. In the current work an effort is made to improve the transverse strength by providing 3D reinforcement in the form of pins and stitching the laminate in thickness direction. Laminates were made of S2-Glass/Vinyl Ester. Specimens of size 3 × 4 inch were subjected to drop-weight impact at energy levels of 20, 31 and 41 Joules. The impacted panels were subjected to vibration tests to determine the stiffness loss through vibration based frequency response function (FRF) measurements. Effect of impact damage on interlaminar shear strength was studied. Results indicate that there is considerable improvement in damage tolerance due to 3D reinforcement.

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Icardi, Ugo, and Laura Ferrero. "Impact and Blast Pulse: Improving Energy Absorption of Fibre-Reinforced Composites Through Optimized Tailoring." In ASME 8th Biennial Conference on Engineering Systems Design and Analysis. ASMEDC, 2006. http://dx.doi.org/10.1115/esda2006-95772.

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This paper tries to conjugate an improvement of stiffness and delamination damage resistance. A number of published results allow us to guess the existence of fibre orientations that are a good compromise for an optimal absorption of the incoming energy and for maintaining of a high stiffness. Optimal absorption is herein intended as a way not involving weak properties, such as interlaminar strength. We seek for an optimal orientation of reinforcement fibres through definition of stationary conditions for bending and shear energy contributions under in-plane variation of plate stiffness coefficients. Our goal is to tune the energy absorption as desired. Two kinds of optimized layers are studied, that are compatible with current production technologies: type 1 reduces bending without substantially increasing the transverse shear stresses, type 2 reduces transverse shear stresses without substantially increasing deflections. Incorporation into the laminates of couples of these layers with opposite features and the same mean properties of those they substitute allows an energy transfer from an unwanted to a wanted mode, as shown by the numerical applications. In this way, the deflections and the stresses inducing delamination damage of laminates subjected to impact and blast pulse loads were reduced, while damping should not substantially change since the variation of the orientation of fibres lies in a range where mild variations of it are induced.

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Pastore, Christopher M., and Frank K. Ko. "Near Net Shape Manufacturing of Composite Engine Components by 3-D Fiber Architecture." In ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1989. http://dx.doi.org/10.1115/89-gt-315.

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Responding to the need for a higher level of through thickness strength, higher damage tolerance, and near net shape manufacturing in structural engine components, there is a worldwide revival in the interest in 3-D fabric preforms. Recent advances in computer aided design, analysis and manufacturing of fully integrated 2-D and 3-D woven, knitted, and braided fibrous structures promises to lead to major advances in composite technology. Through thickness strength imparted to composites by virtue of such integrated reinforcement will open new applications for composites that could not be considered previously, primarily due to the poor transverse strength and interlaminar shear properties of traditional laminated composites. The ability of these structures to conform to shape or assume near net structural shapes promises to simplify manufacturing processes, reduce costs, and enhance design flexibility.

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Elbella, Abdalla, and Santosh Kumar Saride. "Ballistic Impact Response of Composite Systems." In ASME 2006 International Mechanical Engineering Congress and Exposition. ASMEDC, 2006. http://dx.doi.org/10.1115/imece2006-15154.

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Composite materials are widely used in many engineering applications and are an attractive for armor design because of their increased high toughness, impact resistance, stiffness, and strength-to-weight ratios and the ability to tailor their designs to applications. In this paper, numerical simulation of impact on composites is being performed to predict ballistic limit velocities and evaluate the delamination behavior of different composite systems. The normal impact and penetration of blunt rigid projectile on laminated composite targets was developed to estimate the velocity for which the projectile has complete penetration, the ballistic limits and energy absorbed while perforating a given piece of armor. A non-linear, explicit, three dimensional finite element commercial code (ABAQUS) is used to simulate the response of armor targets at V50 impact velocities. The armor test panel is modeled as a multi-layered laminated plate with different composite systems, thickness, and stacking sequence. The three failure modes that represent the three stages of the penetration process namely transverse shear, tensile fiber breakage, and delamination are identified. The ballistic limit curves for different materials, thickness, and orientations are determined. The target interlaminar stress distributions along the thickness are graphically represented. Strain energy, Plastic dissipation and Kinetic dissipation energy curves for the whole model were obtained including thickness effects.

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Tian, Zhenhua, Cara A. C. Leckey, Jeffrey P. Seebo, and Lingyu Yu. "Guided Wave Delamination Detection and Quantification With Wavefield Data Analysis." In ASME 2014 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/smasis2014-7645.

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Unexpected damage can occur in aerospace composites due to impact events or material stress during off-nominal loading events. In particular, laminated composites are susceptible to delamination damage due to weak transverse tensile and interlaminar shear strengths. Developments of reliable and quantitative techniques to detect delamination damage in laminated composites are imperative for safe and functional optimally-designed next-generation composite structures. In this paper, we investigate guided wave interactions with delamination damage and develop quantification algorithms by using wavefield data analysis. The trapped guided waves in the delamination region are observed from the wavefield data and further quantitatively interpreted by using different wavenumber analysis methods. The frequency-wavenumber representation of the wavefield shows that new wavenumbers are present and correlate to trapped waves in the damage region. These new wavenumbers are used to detect and quantify the delamination damage through the wavenumber analysis, which can show how the wavenumber changes as a function of wave propagation distance. The location and spatial duration of new wavenumbers can be identified, providing a useful means not only for detecting the presence of delamination damage but also for estimation of the delamination size. Our method has been applied to detect and quantify real delamination damage with complex geometry (grown using a quasi-static indentation technique). The detection and quantification results show the location, size, and shape of the delamination damage.

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DOSHI, SAGAR M., PAUL D. SAMUEL, MOLLA A. ALI, ANDREW J. STACK, BAZLE Z. (GAMA) HAQUE, JOSEPH M. DEITZEL, and JOHN W. GILLESPIE, JR. "LOW VELOCITY IMPACT EXPERIMENTS OF S-2 GLASS-EPOXY COMPOSITES UNDER DIFFERENT ENVIRONMENTAL CONDITIONS." In Proceedings for the American Society for Composites-Thirty Seventh Technical Conference. Destech Publications, Inc., 2022. http://dx.doi.org/10.12783/asc37/36422.

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S-2 glass-epoxy composites are used in damage tolerant structural applications such as military ground vehicles due to their high specific strength, stiffness, and energy-absorbing capabilities. Composites can be susceptible to delamination failure caused due to high interlaminar shear stresses when subjected to transverse impact loading. While fiber fracture, fiber pullout, matrix cracking, and delaminations are the major damage mechanisms, delamination is a significant energy absorbing failure mode in low-velocity impacts (LVI). LVI leads to a reduction of stiffness and residual strength, which is critical for structural integrity. To improve the delamination resistance, researchers have used various types of interlayers for composites subjected to impacts. In this research, LVI experiments are conducted on composites made using plain weave S-2 glass and SC-15 epoxy resin. Two types of specimens are tested, 'baseline' (without interlayer) and 'interlayer' (with thermoplastic interlayer UAF 472). A Dynatup 9200 drop tower with a hemi-cylindrical 12.7 mm impactor is used. The specimens are impacted (40J) at three temperatures, -55C, RT, and 76C. The stiffness before and after the LVI test is evaluated, and the influence of temperature and impacts on stiffness change is discussed, along with the mechanisms that cause the change in stiffness. The interlayer specimens have significantly smaller delamination areas, and the stiffness loss due to impact is also reduced (compared to baseline) at each temperature. However, since the properties of the resin and the TPU deteriorate at elevated temperatures, there is a drastic stiffness loss in interlayer specimens at elevated temperatures in the pristine, non-impacted samples.

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